Accession Number:

ADA411103

Title:

Hot Firing of a Full Scale Copper Tubular Combustion Chamber

Descriptive Note:

Technical paper

Corporate Author:

PRATT AND WHITNEY WEST PALM BEACH FL GOVERNMENT ENGINES AND SPACE PROPULSION

Personal Author(s):

Report Date:

2002-05-01

Pagination or Media Count:

15.0

Abstract:

This paper describes the chamber design and hot firing test results for a full-scale copper tubular combustion chamber that has future application in a high-thrust, upper-stage expander cycle engine. The Advanced Expander Combustor AEC was developed by Pratt Whitney Space Propulsion under contract with AFRL to support the Integrated High Payoff Rocket Propulsion Technology IHPRPT initiative. The AEC copper tubular design combines high material thermal conductivity and large effective surface area in a structurally compliant coolant channel configuration to achieve significant heat pick-up from the combustion gases to the coolant. AEC hot fire test data analysis confirmed the ability to achieve high thrust in an expander cycle engine using a copper tubular construction. Heat transfer enhancement due to the tubular chamber liner construction was shown to be in the range of 29 to 46 at typical operating conditions compared with a smooth wall copper liner design. Until recently, no significant improvement in chamber tube thermal conductivity was available without an unacceptable sacrifice in material properties such as strength, Low Cycle Fatigue, and oxidationerosion capability. The development of PWA 1177 dispersion strengthened copper addressed this unacceptable trade off. This material provides high strength, high thermal conductivity, and excellent oxidation resistance. The AEC used PWA 1177 in its chamber design to provide the increased heat transfer and resultant energy necessary to support the high thrust required to meet IHPRPTs goals. The technology developed during the AEC fabrication and test program is currently being used by Pratt Whitney in the development of the RL6O, a high-performance 60,000 pound thrust expander cycle engine. 1 table, 11 figures, 6 refs.

Subject Categories:

  • Combustion and Ignition
  • Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE